Rudder-bar for aeroplanes



W. H. McMULLEN.

RUDDER BAR FOR AEROPLANES. APPLICATION HLED SEPT. 28, I918.

i a a I] y I! E 1 W'zZZzam H- McMuZZen:

wilt 1490300 UNITED 'STATES PATENT OFFICE.

WILLIAM H. McMULLEn', or nousrozv, TEXAS.

RUDDER-BAR FOR AEROPLANES.

Specification of Letters Patent.

Patented May 25, 1920.

Application filed September 28, 1918. Serial No. 256,086.

This invention relates to improvementsin aeroplanes and especially to the steering mechanism therefor, the object being to provide means for normally locking the rudder in position so as to permit the aviator to remove his feet from the steering bar, so as to relieve the strain of continual pressure upon the said bar.

Another object is the provision of means carried by the steering bar which is normally engaged with a stationary object and which is released by pressure of the foot upon the bar, so thatwhen it is desired to change the direction of travel of the machine, a pressure of the foot will both release the bar and operate the rudder.

Other objects and advantages of the invention will appear as the following de scription is read in connection with the accompanying drawings, in which the figure shown represents a'plan view of the steering bar of an aeroplane with theinvention applied thereto.

Referring more specifically to the drawings, wherein like characters of reference denote corresponding parts, the steering bar is shown at 10, being mounted upon a vertical post or shaft 11 for pivotal movement. The bar 10 is of the double ended type, that is, provision is made at each end for the reception of the foot of the aviator, such as depressions 12. Each end of the bar 10 is connected to the rudder in the usual manner,

as by wires or cables 13.

Rigidly mounted upon the post or shaft 11, is a disk 14;, which is provided upon its periphery with spaced teeth 15. Pivotally mounted upon the bar 10 as shown at 16,

is an angled lever 17, one end of which is disposed in advance of the foot receiving olepression 12 of the bar 10 and is formed into a stirrup 17, so as to provide a foot pedal.

The opposite end of the lever 17 is provided with a substantially right angular tooth 18, which is disposed radially with respect to the disk 14. This tooth is adapted to enter the depressions 15 of the disk 14: and when so engaged will lock the bar 10 against movement. If desired the .lever 17 may be duplicated upon each side of the pivot point of the bar.

in the use of the invention as shown and described, the aviator is enabled to remove his feet from the steering bar, so as to release his muscles and relieve the strain of continuously holding the barv in position. When the bar is released from the pressure of the foot the said bar will be automatically locked against movement and the rudder will remain in the position placed so that the machine will continue on its course until the latter is changed by releasing the steering bar.

The invention is susceptible of various changes in its form, proportions and minor details of construction and the right is reserved to make such changes as fall within the scope of the appended claim.

Having described the invention, what is claimed is The combination with an airplane steering bar pivotally mounted intermediate its ends upon a stationary pivot and having a toothed disk secured upon said pivot, of a spring controlled locking lever of substantially ,V- shaped formation and pivotally mounted at the point of the V upon the steering bar, a tooth located at one end'of the lever for engagement with the toothed disk and an oil- 'WILLIAM H. MoMULLEN.

a set portion located at the opposite end of the i 

